Airworthiness Directive · Amendment 39-18925 · Fuselage
Airbus Airplanes
This AD applies to Airbus Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes, certificated in any category.
We are adopting a new airworthiness directive (AD) for certain Airbus Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes. This AD was prompted by a full scale fatigue test campaign on these airplanes in the context of the extended service goal. This AD requires inspections of the affected frame locations, and repair if necessary. We are issuing this AD to address the unsafe condition on these products.
At the applicable time specified in table 1 to the introductory text of paragraph (g) of this AD, do a rototest inspection for cracking at frame (FR) 35.1, FR 35.2, and FR 35.3 on the LH and RH sides, in accordance with the Accomplishment Instructions of the Airbus service information specified in paragraphs (g)(1), (g)(2), (g)(3), (g)(4), (g)(5), and (g)(6) of this AD. Repeat the inspection thereafter at intervals not to exceed 5,300 flight cycles.
| Airplane accumulated total flight cycles at the effective date of this AD | Compliance time |
|---|---|
| For airplanes with 18,300 total flight cycles or less | Before exceeding 18,300 total flight cycles, or within 5,300 flight cycles after the effective date of this AD, whichever occurs later. |
| For airplanes with more than 18,300 total flight cycles | Before exceeding 23,600 total flight cycles, or within 2,100 flight cycles after the effective date of this AD, whichever occurs later. |
(1) Airbus Service Bulletin A320-53-1308, dated November 4, 2015 (FR 35.1 LH side).
(2) Airbus Service Bulletin A320-53-1309, dated November 4, 2015 (FR 35.1 RH side).
(3) Airbus Service Bulletin A320-53-1310, dated November 4, 2015 (FR 35.2 LH side).
(4) Airbus Service Bulletin A320-53-1311, dated November 4, 2015 (FR 35.2 RH side).
(5) Airbus Service Bulletin A320-53-1312, dated November 4, 2015 (FR 35.3 LH side).
(6) Airbus Service Bulletin A320-53-1313, dated November 4, 2015 (FR 35.3 RH side).
If any crack is found during any inspection required by the introductory text to paragraph (g) of this AD: Before further flight, repair using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (DOA). Although the service information specified in paragraph (g) of this AD specifies to contact Airbus for repair instructions, and specifies that action as “RC” (Required for Compliance), this AD requires repair as specified in this paragraph. Repair of an airplane as required by this paragraph does not constitute terminating action for the repetitive inspections required by the introductory text to paragraph (g) of this AD for that airplane, unless specified otherwise in the repair instructions approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA.
